Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 76-MP-120 (fx76mp120-il)

FX 76-MP-120 - Wortmann FX 76-MP-120 airfoil


Airfoil fx76mp120-il
Details Dat file Parser  
(fx76mp120-il) FX 76-MP-120
Wortmann FX 76-MP-120 airfoil
Max thickness 12.1% at 33.9% chord.
Max camber 7.6% at 46.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 76-MP-120
1.00000     0.00000
0.99893     0.00056
0.99572     0.00272
0.99039     0.00521
0.98296     0.00815
0.97347     0.01154
0.96194     0.01553
0.94844     0.02008
0.93301     0.02517
0.91573     0.03079
0.89668     0.03694
0.87592     0.04364
0.85355     0.05087
0.82967     0.05863
0.80438     0.06688
0.77779     0.07552
0.75000     0.08430
0.72114     0.09291
0.69134     0.10106
0.66072     0.10851
0.62941     0.11511
0.59755     0.12076
0.56526     0.12543
0.53270     0.12912
0.50000     0.13186
0.46730     0.13366
0.43474     0.13456
0.40245     0.13457
0.37059     0.13369
0.33928     0.13195
0.30866     0.12936
0.27886     0.12593
0.25000     0.12169
0.22221     0.11668
0.19562     0.11094
0.17033     0.10451
0.14645     0.09746
0.12408     0.08983
0.10332     0.08169
0.08427     0.07311
0.06699     0.06418
0.05156     0.05503
0.03806     0.04583
0.02653     0.03673
0.01704     0.02791
0.00961     0.01955
0.00428     0.01191
0.00107     0.00523
0.00000     0.00000
0.00107     -0.00444
0.00428     -0.00807
0.00961     -0.01097
0.01704     -0.01319
0.02653     -0.01458
0.03806     -0.01514
0.05156     -0.01494
0.06699     -0.01409
0.08427     -0.01268
0.10332     -0.01088
0.12408     -0.00879
0.14645     -0.00646
0.17033     -0.00398
0.19562     -0.00141
0.22221     0.00119
0.25000     0.00376
0.27886     0.00625
0.30866     0.00862
0.33928     0.01083
0.37059     0.01287
0.40245     0.01472
0.43474     0.01637
0.46730     0.01783
0.50000     0.01909
0.53270     0.02016
0.56526     0.02105
0.59755     0.02178
0.62941     0.02237
0.66072     0.02284
0.69134     0.02320
0.72114     0.02345
0.75000     0.02357
0.77779     0.02346
0.80438     0.02306
0.82967     0.02233
0.85355     0.02123
0.87592     0.01978
0.89668     0.01801
0.91573     0.01595
0.93301     0.01369
0.94844     0.01128
0.96194     0.00881
0.97347     0.00633
0.98296     0.00396
0.99039     0.00187
0.99572     0.00053
0.99893     0.00004
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 630 AIRFOILPreviewDetails
DAE-21 AIRFOILPreviewDetails
GOE 447 AIRFOILPreviewDetails
DAE-11 AIRFOILPreviewDetails
GOE 366 AIRFOILPreviewDetails
DAE-31 AIRFOILPreviewDetails
GOE 332 (PFALZ 61) AIRFOILPreviewDetails
GOE 501 AIRFOILPreviewDetails
GOE 528 AIRFOILPreviewDetails
GOE 405 AIRFOILPreviewDetails

Polars for FX 76-MP-120 (fx76mp120-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx76mp120-il50,00096.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp120-il50,000516.5 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp120-il100,000942.9 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp120-il100,000541.8 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp120-il200,000985.9 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp120-il200,000588.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp120-il500,0009147.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp120-il500,0005141.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp120-il1,000,0009192.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp120-il1,000,0005174 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit